US9435221B2 - Turbomachine airfoil positioning - Google Patents
Turbomachine airfoil positioning Download PDFInfo
- Publication number
- US9435221B2 US9435221B2 US13/963,689 US201313963689A US9435221B2 US 9435221 B2 US9435221 B2 US 9435221B2 US 201313963689 A US201313963689 A US 201313963689A US 9435221 B2 US9435221 B2 US 9435221B2
- Authority
- US
- United States
- Prior art keywords
- airfoil
- turbomachine
- row
- diffuser
- rows
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active, expires
Links
- 238000000034 method Methods 0.000 claims description 31
- 239000012530 fluid Substances 0.000 claims description 10
- 238000011144 upstream manufacturing Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 230000002123 temporal effect Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/003—Arrangements for testing or measuring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
Definitions
- Turbomachines such as turbines, engines, and compressors, include pluralities of stationary vanes and rotating blades. These are typically arranged in alternating stacked airfoil rows disposed around and along the longitudinal axis of the machine, with the vanes affixed to the turbine casing and the blades affixed to a disk connected to a shaft. Efforts have been made to improve the efficiency of such machines by indexing or “clocking” the relative circumferential positions of airfoils in one row to the circumferential positions of airfoils in adjacent or nearby rows. Typically, such improvement is achieved by reducing the impact of vane wake on the rotating blades.
- Some turbomachines such as gas turbines, include a diffuser disposed adjacent the final stage of the turbine. Such a diffuser is configured to decelerate the exhaust flow, converting dynamic energy to a static pressure rise, and do so more efficiently when circumferential variation in the flow entering the diffuser is reduced.
- Known turbomachines and clocking methods do not address or consider the circumferential variation of the flow field entering the diffuser. In fact, some clocking methods may increase circumferential variation in order to provide efficiencies in other areas of the turbine, such as increased energy efficiency or decreased vibration and stress in the airfoils.
- Embodiments of the invention relate generally to turbomachines and, more particularly, to the clocking of turbomachine airfoils to reduce airflow pressure variations entering a diffuser of the turbomachine.
- the invention provides a turbomachine comprising: a diffuser; a plurality of airfoil rows, including: a first airfoil row adjacent the diffuser, the first airfoil row being of a first type selected from a group consisting of: stationary vanes and rotating blades; a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type; and a third airfoil row of the first type adjacent the second airfoil row, wherein at least one of the plurality of airfoil rows is clocked, relative to another airfoil row of the turbomachine, reducing variations in airflow circumferential pressure at at least one spanwise location in the diffuser adjacent the first airfoil row in an operative state of the turbomachine.
- the invention provides a method of reducing variation in airflow pressure entering a diffuser of a turbomachine, the method comprising: calculating airflow across at least three airfoil rows of the turbomachine, the at least three airfoil rows including: a first airfoil row adjacent a diffuser of the turbomachine, the first airfoil row being of a first type selected from a group consisting of: stationary vanes and rotating blades; a second airfoil row adjacent the first airfoil row, the second airfoil row being of a second type different from the first type; and a third airfoil row of the first type adjacent the second airfoil row; evaluating a pressure variation at at least one spanwise location of the diffuser; and determining whether the pressure variation is within a predetermined target.
- the invention provides a method of reducing variation in airflow pressure entering a diffuser of a turbomachine, the method comprising: calculating airflow across at least airfoil rows of the turbomachine; evaluating a first pressure variation at at least one spanwise location of a diffuser of the turbomachine; changing a relative clocking position of at least one of the three airfoil rows; recalculating airflow across the at least three airfoil rows; evaluating a second pressure variation at the at least one spanwise location of the diffuser; determining whether the second pressure variation is less than the first pressure variation; and in the case that the second pressure variation is less than the first pressure variation, operating the turbomachine using the changed relative clocking position of the at least one airfoil row.
- FIG. 1 shows a schematic view of airfoils and a diffuser of a turbomachine.
- FIG. 2 shows a schematic view of a cross-sectional shape of a diffuser at a position adjacent an airfoil row nearest the diffuser.
- FIG. 3 is a graphical representation of pressures measured across the radial span of a diffuser.
- FIG. 4 shows a flow diagram of a method according to an embodiment of the invention.
- FIG. 5 is a graphical representation of pressure variations at a surface of a diffuser before and after airfoil clocking according to an embodiment of the invention.
- FIG. 1 is a schematic representation of neighboring rows 110 , 120 , 130 , 140 , 150 , 160 of airfoils as may be found, for example, in a gas turbine.
- Row 160 is the last (i.e., most downstream or terminal) airfoil row of a turbine and sits adjacent a diffuser 180 .
- Rows 110 , 130 , and 150 show stationary vanes.
- Rows 120 , 140 , and 160 show blades that, in operation, rotate in direction R.
- rows 110 , 130 , and 150 may comprise blades and rows 120 , 140 , and 160 may comprise vanes.
- rows 110 , 120 , 130 , 140 , 150 , and 160 which will be referred to below as a first, second, third, fourth, fifth, and sixth row, respectively, are intended to describe relative ordering of the rows. That is, a turbine or other turbomachine according to various embodiments of the invention may include more than the six airfoil rows shown in FIG. 1 and methods according to various embodiments of the invention are applicable to turbomachines having more or fewer than six airfoil rows. As will be described below in greater detail, methods according to embodiments of the invention are applicable to turbines or other turbomachines having a diffuser and three or more rows of airfoils.
- FIG. 1 The airfoils and their shapes shown in FIG. 1 are merely illustrative and should not be viewed as limiting the scope of the invention. Methods according to embodiments of the invention, as well as turbomachines constructed or configured according to embodiments of the invention, may include airfoils of any number, shape, and size.
- the pitch of the airfoils may be described as the circumferential distance between corresponding features of adjacent airfoils of the same row.
- pitch P is the distance between the high curvature point of vane 10 and vane 12 .
- Other features may be used to define pitch P, of course.
- pitch P may be measured from leading edge to leading edge of adjacent vanes, which would yield the same distance in a cylindrical flow path as that from trailing edge to trailing edge.
- first row 110 is clocked with respect to row 130 , with vane 30 offset from vane 10 by distance ⁇ .
- Distance ⁇ may be expressed, for example, as a function—e.g., 0.1, 0.2, 0.3, etc.—of pitch P. As shown in FIG. 1 , distance ⁇ may be, for example, 0.3 of pitch P.
- FIG. 1 also shows a plurality of fluid flows A, B, C, D, and E through rows 110 , 120 , 130 , 140 , 150 , and 160 to diffuser 180 .
- FIG. 2 is a schematic representation of a cross-section of diffuser 180 adjacent fourth row 140 ( FIG. 1 ). Fluid flows enter diffuser 180 across span S, extending from an inner circumference C 1 —0% span—to an outer circumference C 2 —100% span. Circumferential variations in pressure flow into diffuser 180 decrease overall machine efficiency.
- FIG. 3 shows a graph of pressures measured across the span of a diffuser of a typical turbine.
- Minimum pressures 182 measured from 0% span to 100% span are significantly less than maximum pressures 186 .
- Average pressures 184 are, as expected, intermediate minimum pressures 182 and maximum pressures 186 . Any steps taken to reduce the difference between minimum pressures 182 and maximum pressures 186 will improve the efficiencies of both the diffuser and the turbomachine overall.
- the clocking of late stage airfoils includes clocking at least two of three adjacent airfoil rows nearest the diffuser.
- third and fifth rows 130 , 150 may be clocked with respect to each other.
- second and fourth rows 120 , 140 may also be clocked with respect to each other.
- clocking of airfoil rows may be carried out with respect to pairs or groups of stationary vane rows as well as with respect to pairs or groups of rotating blade rows.
- FIG. 4 shows a flow diagram of a method of clocking airfoils to reduce variation in diffuser inflow according to an embodiment of the invention.
- airflows across at least three airfoil rows nearest the diffuser are calculated.
- the at least three airfoil rows may include a pair of stationary vane rows and an intervening rotating blade row or a pair of rotating blade rows and an intervening stationary vane row.
- the at least three airfoil rows across which airflow would be calculated at S 1 include rows 140 , 150 , and 160 .
- the calculation of airflows across turbomachine airfoils typically relies upon computational fluid dynamics (CFD) to model turbulence.
- CFD computational fluid dynamics
- this may include employing the Navier-Stokes or Reynolds-averaged Navier-Stokes solver equations—the basic governing equations for viscous, heat conducting fluids.
- Other solver equations may also be employed for any number of reasons, as will be appreciated by one skilled in the art.
- the Navier-Stokes solver equations are a set of differential equations, including a continuity equation for the conservation of mass, conservation of momentum equations, and a conservation of energy equation. These equations employ spatial and temporal variables, as well as pressure, temperature, and density variables.
- CFD equations and techniques may be used.
- solver equations may be employed and the use of other CFD equations, techniques, or solver equations is intended to be within the scope of the invention.
- pressure variation at the diffuser is evaluated at one or more span locations of interest.
- pressure variations may be evaluated at representative locations across the entire span of the diffuser, from 0% span (at its inner circumference—C 1 in FIG. 2 ) to 100% span (at its outer circumference—C 2 in FIG. 2 ).
- pressure variation may be evaluated at a single location, e.g., at 0% span.
- pressure variation at the diffuser will not be eliminated entirely. As such, there will generally be some level of pressure variation at the diffuser that will be acceptable for a particular turbomachine. This may be, for example, a percentage deviation from an average pressure. Clocking airfoils according to embodiments of the invention will therefore typically seek to reduce pressure variation to a point equal to or less than such a targeted pressure variation.
- the relative clocking position of at least one upstream row of airfoils of similar type is changed (e.g., where the airfoil row adjacent the diffuser is a blade row, the relative clocking position of an upstream row of blades is changed).
- changing the clocking at S 3 may include changing the clocking of the blade of row 140 relative to the blades of row 160 as a function of pitch P.
- changing the clocking at S 3 may include changing the clocking of row 130 relative to row 150 .
- changing the clocking of row 130 relative to row 150 may include changing the relative positions of upstream rows of airfoils in carrying out S 3 .
- flow is recalculated at S 4 using the changed clocking position and the pressure variation is reevaluated at S 5 .
- the pressure variation at S 5 is within a targeted pressure variation (e.g., 5% of the average pressure measured). If so (i.e., YES at S 6 ), the changed clocking positions may be used in operation of the turbomachine at S 7 . If not (i.e., NO at S 6 ), S 3 through S 6 may be iteratively looped until the pressure variation at S 5 is found to be within the targeted pressure variation at S 6 .
- a targeted pressure variation e.g., 5% of the average pressure measured
- the targeted pressure variation at S 6 may be an absolute value (e.g., an amount of variation in p.s.i.), an amount of decrease in pressure variation (e.g., a decrease of 1%, 2%, 3%, etc.) with respect to the pressure variation at S 2 , or any pressure variation value less than the pressure variation at S 2 .
- an absolute value e.g., an amount of variation in p.s.i.
- an amount of decrease in pressure variation e.g., a decrease of 1%, 2%, 3%, etc.
- FIG. 5 shows a graphical comparison of pressure variation (measured pressure/average pressure) as a function of clocking position (pitch) before 190 and after 192 clocking according to an embodiment of the invention.
- 190 and after 192 clocking should be understood to mean before and after clocking according to an embodiment of the invention, not necessarily before and after any clocking of the airfoils of the turbomachine. That is, embodiments of the invention may be employed to clock airfoils in rows nearest a diffuser 180 after the airfoils of the turbomachine have otherwise been clocked for purposes other than reducing variation in airflow at the diffuser. As noted above, such other purposes often involve the clocking of “upstream” airfoil rows furthest from the diffuser. As such, clocking methods according to embodiments of the invention may be employed in combination with other clocking methods known in the art.
- pressure variation was calculated to be A %, but was reduced to approximately B % by employing a clocking method according to an embodiment of the invention.
Abstract
Description
Claims (18)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/963,689 US9435221B2 (en) | 2013-08-09 | 2013-08-09 | Turbomachine airfoil positioning |
DE201410110315 DE102014110315A1 (en) | 2013-08-09 | 2014-07-22 | A blade positioning |
JP2014157284A JP6514455B2 (en) | 2013-08-09 | 2014-08-01 | Turbomachinery airfoil positioning |
CH01203/14A CH708447A2 (en) | 2013-08-09 | 2014-08-07 | Turbomachine with blade positioning. |
CN201410389920.7A CN105019949B (en) | 2013-08-09 | 2014-08-08 | Turbo-machine airfoil positions |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/963,689 US9435221B2 (en) | 2013-08-09 | 2013-08-09 | Turbomachine airfoil positioning |
Publications (2)
Publication Number | Publication Date |
---|---|
US20150044017A1 US20150044017A1 (en) | 2015-02-12 |
US9435221B2 true US9435221B2 (en) | 2016-09-06 |
Family
ID=52388949
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/963,689 Active 2034-09-09 US9435221B2 (en) | 2013-08-09 | 2013-08-09 | Turbomachine airfoil positioning |
Country Status (5)
Country | Link |
---|---|
US (1) | US9435221B2 (en) |
JP (1) | JP6514455B2 (en) |
CN (1) | CN105019949B (en) |
CH (1) | CH708447A2 (en) |
DE (1) | DE102014110315A1 (en) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102014204346A1 (en) * | 2014-03-10 | 2015-09-10 | Rolls-Royce Deutschland Ltd & Co Kg | Method for producing a double-row paddle wheel for a turbomachine and double-row paddle wheel |
US20160177835A1 (en) * | 2014-12-22 | 2016-06-23 | Pratt & Whitney Canada Corp. | Gas turbine engine with angularly offset turbine vanes |
FR3044412B1 (en) * | 2015-11-30 | 2018-11-09 | Safran Aircraft Engines | INSTRUMED VEIN OF TURBOMACHINE |
Citations (118)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2663493A (en) | 1949-04-26 | 1953-12-22 | A V Roe Canada Ltd | Blading for compressors, turbines, and the like |
US3347520A (en) | 1966-07-12 | 1967-10-17 | Jerzy A Oweczarek | Turbomachine blading |
US3572962A (en) | 1969-06-02 | 1971-03-30 | Canadian Patents Dev | Stator blading for noise reduction in turbomachinery |
US3643426A (en) | 1969-06-30 | 1972-02-22 | Ingvar Janelid | Powerplant driven by a gas turbine, and a method of operating such a powerplant |
US3734639A (en) | 1968-01-25 | 1973-05-22 | Gen Motors Corp | Turbine cooling |
US3745629A (en) | 1972-04-12 | 1973-07-17 | Secr Defence | Method of determining optimal shapes for stator blades |
JPS54114618A (en) | 1978-02-28 | 1979-09-06 | Toshiba Corp | Moving and stator blades arranging method of turbine |
JPS54114619A (en) | 1978-02-28 | 1979-09-06 | Toshiba Corp | Natural frequency adjusting method of turbine blade |
US4259842A (en) | 1978-12-11 | 1981-04-07 | General Electric Company | Combustor liner slot with cooled props |
US4284388A (en) | 1975-11-03 | 1981-08-18 | Polska Akademia Nauk, Instytut Maszyn Przeplywowych | Moving blade for thermic axial turbomachines |
US4504189A (en) | 1982-11-10 | 1985-03-12 | Rolls-Royce Limited | Stator vane for a gas turbine engine |
US4585395A (en) | 1983-12-12 | 1986-04-29 | General Electric Company | Gas turbine engine blade |
US4616975A (en) | 1984-07-30 | 1986-10-14 | General Electric Company | Diaphragm for a steam turbine |
US4619580A (en) | 1983-09-08 | 1986-10-28 | The Boeing Company | Variable camber vane and method therefor |
US4714407A (en) | 1984-09-07 | 1987-12-22 | Rolls-Royce Plc | Aerofoil section members for turbine engines |
US4786016A (en) | 1986-04-30 | 1988-11-22 | United Technologies Corporation | Bodies with reduced surface drag |
US4802821A (en) | 1986-09-26 | 1989-02-07 | Bbc Brown Boveri Ag | Axial flow turbine |
US4809498A (en) | 1987-07-06 | 1989-03-07 | General Electric Company | Gas turbine engine |
US4844689A (en) | 1986-07-04 | 1989-07-04 | Rolls-Royce Plc | Compressor and air bleed system |
US4896510A (en) | 1987-02-06 | 1990-01-30 | General Electric Company | Combustor liner cooling arrangement |
US4968216A (en) | 1984-10-12 | 1990-11-06 | The Boeing Company | Two-stage fluid driven turbine |
US5226278A (en) | 1990-12-05 | 1993-07-13 | Asea Brown Boveri Ltd. | Gas turbine combustion chamber with improved air flow |
US5249922A (en) | 1990-09-17 | 1993-10-05 | Hitachi, Ltd. | Apparatus of stationary blade for axial flow turbine, and axial flow turbine |
US5274991A (en) | 1992-03-30 | 1994-01-04 | General Electric Company | Dry low NOx multi-nozzle combustion liner cap assembly |
US5342170A (en) | 1992-08-29 | 1994-08-30 | Asea Brown Boveri Ltd. | Axial-flow turbine |
US5406786A (en) | 1993-07-16 | 1995-04-18 | Air Products And Chemicals, Inc. | Integrated air separation - gas turbine electrical generation process |
US5486091A (en) | 1994-04-19 | 1996-01-23 | United Technologies Corporation | Gas turbine airfoil clocking |
US5749218A (en) | 1993-12-17 | 1998-05-12 | General Electric Co. | Wear reduction kit for gas turbine combustors |
US5785498A (en) | 1994-09-30 | 1998-07-28 | General Electric Company | Composite fan blade trailing edge reinforcement |
US5813828A (en) | 1997-03-18 | 1998-09-29 | Norris; Thomas R. | Method and apparatus for enhancing gas turbo machinery flow |
US6174129B1 (en) | 1999-01-07 | 2001-01-16 | Siemens Westinghouse Power Corporation | Turbine vane clocking mechanism and method of assembling a turbine having such a mechanism |
US6209325B1 (en) | 1996-03-29 | 2001-04-03 | European Gas Turbines Limited | Combustor for gas- or liquid-fueled turbine |
EP1130321A1 (en) | 2000-02-25 | 2001-09-05 | General Electric Company | Combustor liner cooling thimbles and related method |
US6345493B1 (en) | 1999-06-04 | 2002-02-12 | Air Products And Chemicals, Inc. | Air separation process and system with gas turbine drivers |
US20020048510A1 (en) | 2000-10-23 | 2002-04-25 | Fiatavio S.P.A. | Method of positioning turbine stage arrays, particularly for aircraft engines |
US6402458B1 (en) * | 2000-08-16 | 2002-06-11 | General Electric Company | Clock turbine airfoil cooling |
US6409126B1 (en) | 2000-11-01 | 2002-06-25 | Lockhead Martin Corporation | Passive flow control of bluff body wake turbulence |
US6428281B1 (en) | 1999-08-18 | 2002-08-06 | Snecma Moteurs | Turbine vane with enhanced profile |
US6435814B1 (en) | 2000-05-16 | 2002-08-20 | General Electric Company | Film cooling air pocket in a closed loop cooled airfoil |
US6438961B2 (en) | 1998-02-10 | 2002-08-27 | General Electric Company | Swozzle based burner tube premixer including inlet air conditioner for low emissions combustion |
US6442941B1 (en) | 2000-09-11 | 2002-09-03 | General Electric Company | Compressor discharge bleed air circuit in gas turbine plants and related method |
US6446438B1 (en) | 2000-06-28 | 2002-09-10 | Power Systems Mfg., Llc | Combustion chamber/venturi cooling for a low NOx emission combustor |
US20020124572A1 (en) | 2001-03-12 | 2002-09-12 | Anthony Pidcock | Combustion apparatus |
EP1247938A2 (en) | 2001-03-30 | 2002-10-09 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Clocking of stator- or rotorblades |
US6491493B1 (en) | 1998-06-12 | 2002-12-10 | Ebara Corporation | Turbine nozzle vane |
US6540478B2 (en) | 2000-10-27 | 2003-04-01 | Mtu Aero Engines Gmbh | Blade row arrangement for turbo-engines and method of making same |
US6554562B2 (en) | 2001-06-15 | 2003-04-29 | Honeywell International, Inc. | Combustor hot streak alignment for gas turbine engine |
US6584779B2 (en) | 2000-04-19 | 2003-07-01 | General Electric Company | Combustion turbine cooling media supply method |
US20030136102A1 (en) | 2002-01-22 | 2003-07-24 | Snecma Moteurs | Diffuser for terrestrial or aviation gas turbine |
US6598398B2 (en) | 1995-06-07 | 2003-07-29 | Clean Energy Systems, Inc. | Hydrocarbon combustion power generation system with CO2 sequestration |
US6602458B1 (en) | 2000-06-28 | 2003-08-05 | Rubbermaid Incorporated | Reduced flash molding |
US6626635B1 (en) | 1998-09-30 | 2003-09-30 | General Electric Company | System for controlling clearance between blade tips and a surrounding casing in rotating machinery |
US6772595B2 (en) | 2002-06-25 | 2004-08-10 | Power Systems Mfg., Llc | Advanced cooling configuration for a low emissions combustor venturi |
US6824710B2 (en) | 2000-05-12 | 2004-11-30 | Clean Energy Systems, Inc. | Working fluid compositions for use in semi-closed brayton cycle gas turbine power systems |
EP1482246A1 (en) | 2003-05-30 | 2004-12-01 | Siemens Aktiengesellschaft | Combustion chamber |
US6887042B2 (en) | 2001-01-12 | 2005-05-03 | Mitsubishi Heavy Industries, Ltd. | Blade structure in a gas turbine |
US6899081B2 (en) | 2002-09-20 | 2005-05-31 | Visteon Global Technologies, Inc. | Flow conditioning device |
US6905307B2 (en) | 2001-08-10 | 2005-06-14 | Honda Giken Kogyo Kabushiki Kaisha | Stationary vanes for turbines and method for making the same |
US6913441B2 (en) | 2003-09-04 | 2005-07-05 | Siemens Westinghouse Power Corporation | Turbine blade ring assembly and clocking method |
US20050172607A1 (en) | 2003-05-16 | 2005-08-11 | Koichi Ishizaka | Exhaust diffuser for axial-flow turbine |
US6935116B2 (en) | 2003-04-28 | 2005-08-30 | Power Systems Mfg., Llc | Flamesheet combustor |
US20050206196A1 (en) | 2002-09-20 | 2005-09-22 | The Regents Of The University Of California | Apparatus and method for reducing drag of a bluff body in ground effect using counter-rotating vortex pairs |
US6958383B2 (en) | 1998-02-26 | 2005-10-25 | Aventis Pharma S. A. | Streptogramin derivatives, preparation method and compositions containing same |
USD511377S1 (en) | 2002-07-01 | 2005-11-08 | Donaldson Company, Inc. | Inlet air filter hood module for gas turbine systems |
US6986639B2 (en) | 2002-08-09 | 2006-01-17 | Honda Giken Kogyo Kabushiki Kaisha | Stator blade for an axial flow compressor |
US7007478B2 (en) | 2004-06-30 | 2006-03-07 | General Electric Company | Multi-venturi tube fuel injector for a gas turbine combustor |
US20060101801A1 (en) | 2004-11-18 | 2006-05-18 | Siemens Westinghouse Power Corporation | Combustor flow sleeve with optimized cooling and airflow distribution |
US7089742B2 (en) | 2000-02-29 | 2006-08-15 | Rolls-Royce Plc | Wall elements for gas turbine engine combustors |
US7121792B1 (en) | 2003-03-27 | 2006-10-17 | Snecma Moteurs | Nozzle vane with two slopes |
US20060283189A1 (en) | 2005-06-15 | 2006-12-21 | General Electric Company | Axial flow sleeve for a turbine combustor and methods of introducing flow sleeve air |
US20070025836A1 (en) | 2005-07-28 | 2007-02-01 | General Electric Company | Cooled shroud assembly and method of cooling a shroud |
CN1955440A (en) | 2005-10-28 | 2007-05-02 | 中国科学院工程热物理研究所 | Three-D sequential effect maximization method for multi-stage turbomachine |
US7217101B2 (en) | 2003-10-15 | 2007-05-15 | Alstom Technology Ltd. | Turbine rotor blade for gas turbine engine |
US20070130958A1 (en) | 2005-12-08 | 2007-06-14 | Siemens Power Generation, Inc. | Combustor flow sleeve attachment system |
CN101050722A (en) | 2006-04-07 | 2007-10-10 | 孙敏超 | Changeable outlet flow section turbine jet nozzle ring |
US20070251240A1 (en) | 2006-04-13 | 2007-11-01 | General Electric Company | Forward sleeve retainer plate and method |
US7340129B2 (en) | 2004-08-04 | 2008-03-04 | Colorado State University Research Foundation | Fiber laser coupled optical spark delivery system |
CN101173673A (en) | 2007-11-29 | 2008-05-07 | 北京航空航天大学 | Big and small impeller vane impeller with non-homogeneously distributed blades along circumference and compressor machine |
US7373773B2 (en) | 2003-09-04 | 2008-05-20 | Hitachi, Ltd. | Gas turbine installation, cooling air supplying method and method of modifying a gas turbine installation |
US7412129B2 (en) | 2004-08-04 | 2008-08-12 | Colorado State University Research Foundation | Fiber coupled optical spark delivery system |
US7410343B2 (en) | 2002-12-09 | 2008-08-12 | Mitsubishi Heavy Industries, Ltd. | Gas turbine |
CN101296842A (en) | 2005-10-17 | 2008-10-29 | 贝尔直升机特克斯特龙有限公司 | Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft |
US20090155062A1 (en) | 2007-12-14 | 2009-06-18 | Snecma | Method of designing a multistage turbine for a turbomachine |
US20090223228A1 (en) | 2007-08-15 | 2009-09-10 | Carey Edward Romoser | Method and apparatus for combusting fuel within a gas turbine engine |
US20090320484A1 (en) | 2007-04-27 | 2009-12-31 | Benjamin Paul Lacy | Methods and systems to facilitate reducing flashback/flame holding in combustion systems |
US7654320B2 (en) | 2006-04-07 | 2010-02-02 | Occidental Energy Ventures Corp. | System and method for processing a mixture of hydrocarbon and CO2 gas produced from a hydrocarbon reservoir |
EP2154431A2 (en) | 2008-08-14 | 2010-02-17 | Alstom Technology Ltd | Thermal machine |
US20100054922A1 (en) * | 2008-09-04 | 2010-03-04 | General Electric Company | Turbine airfoil clocking |
US20100054929A1 (en) * | 2008-09-04 | 2010-03-04 | General Electric Company | Turbine airfoil clocking |
US20100111684A1 (en) | 2008-10-31 | 2010-05-06 | General Electric Company | Turbine airfoil clocking |
US20100122538A1 (en) | 2008-11-20 | 2010-05-20 | Wei Ning | Methods, apparatus and systems concerning the circumferential clocking of turbine airfoils in relation to combustor cans and the flow of cooling air through the turbine hot gas flowpath |
US7758306B2 (en) | 2006-12-22 | 2010-07-20 | General Electric Company | Turbine assembly for a gas turbine engine and method of manufacturing the same |
US7758297B2 (en) | 2005-05-10 | 2010-07-20 | Mtu Aero Engines Gmbh | Method for flow optimization in multi-stage turbine-type machines |
US7762074B2 (en) | 2006-04-04 | 2010-07-27 | Siemens Energy, Inc. | Air flow conditioner for a combustor can of a gas turbine engine |
US20100287943A1 (en) | 2009-05-14 | 2010-11-18 | General Electric Company | Methods and systems for inducing combustion dynamics |
US20100326082A1 (en) | 2009-06-30 | 2010-12-30 | Willy Steve Ziminsky | Methods and apparatus for combustor fuel circuit for ultra low calorific fuels |
US7896645B2 (en) | 2008-05-30 | 2011-03-01 | Universal Cleanair Technologies | Three phased combustion system |
US20110107766A1 (en) | 2009-11-11 | 2011-05-12 | Davis Jr Lewis Berkley | Combustor assembly for a turbine engine with enhanced cooling |
US20110189003A1 (en) | 2009-03-19 | 2011-08-04 | Mitsubishi Heavy Industries, Ltd. | Gas turbine |
US20110197586A1 (en) | 2010-02-15 | 2011-08-18 | General Electric Company | Systems and Methods of Providing High Pressure Air to a Head End of a Combustor |
US20110214429A1 (en) | 2010-03-02 | 2011-09-08 | General Electric Company | Angled vanes in combustor flow sleeve |
US20120051894A1 (en) | 2010-08-31 | 2012-03-01 | General Electric Company | Turbine assembly with end-wall-contoured airfoils and preferenttial clocking |
US20120085100A1 (en) | 2010-10-11 | 2012-04-12 | General Electric Company | Combustor with a Lean Pre-Nozzle Fuel Injection System |
US20120159954A1 (en) | 2010-12-21 | 2012-06-28 | Shoko Ito | Transition piece and gas turbine |
US20120167586A1 (en) | 2011-01-05 | 2012-07-05 | Donald Mark Bailey | Fuel Nozzle Passive Purge Cap Flow |
US20120186255A1 (en) | 2011-01-24 | 2012-07-26 | General Electric Company | System for pre-mixing in a fuel nozzle |
US8234872B2 (en) | 2009-05-01 | 2012-08-07 | General Electric Company | Turbine air flow conditioner |
US20120247118A1 (en) | 2011-03-28 | 2012-10-04 | General Electric Company | Combustor crossfire tube |
US8286347B2 (en) | 2007-02-27 | 2012-10-16 | Snecma | Method for reducing vibration levels of a bladed wheel in a turbomachine |
US8307657B2 (en) | 2009-03-10 | 2012-11-13 | General Electric Company | Combustor liner cooling system |
US20120297785A1 (en) | 2011-05-24 | 2012-11-29 | General Electric Company | System and method for flow control in gas turbine engine |
US8425185B2 (en) | 2009-02-25 | 2013-04-23 | Hitachi, Ltd. | Transonic blade |
US20130115566A1 (en) | 2011-11-04 | 2013-05-09 | General Electric Company | Combustor having wake air injection |
US8540490B2 (en) | 2008-06-20 | 2013-09-24 | General Electric Company | Noise reduction in a turbomachine, and a related method thereof |
US20140020395A1 (en) | 2012-07-23 | 2014-01-23 | General Electric Company | Method for modifying gas turbine performance |
US20140041357A1 (en) | 2011-10-19 | 2014-02-13 | Anthony J. Malandra | Exhaust diffuser including flow mixing ramp for a gas turbine engine |
US20140072433A1 (en) | 2012-09-10 | 2014-03-13 | General Electric Company | Method of clocking a turbine by reshaping the turbine's downstream airfoils |
US8707672B2 (en) | 2010-09-10 | 2014-04-29 | General Electric Company | Apparatus and method for cooling a combustor cap |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2004011458A (en) * | 2002-06-04 | 2004-01-15 | Ishikawajima Harima Heavy Ind Co Ltd | Stationary blade clocking device and its position control method |
JP2005220797A (en) * | 2004-02-05 | 2005-08-18 | Mitsubishi Heavy Ind Ltd | Turbine |
JP2006138250A (en) * | 2004-11-11 | 2006-06-01 | Mitsubishi Heavy Ind Ltd | Axial flow rotary fluid machine |
US7555871B1 (en) * | 2005-02-03 | 2009-07-07 | Guardian, Llc | Window framing system for sliding windows |
US8439626B2 (en) * | 2008-12-29 | 2013-05-14 | General Electric Company | Turbine airfoil clocking |
JP2011241791A (en) * | 2010-05-20 | 2011-12-01 | Kawasaki Heavy Ind Ltd | Turbine of gas turbine engine |
US20130081402A1 (en) * | 2011-10-03 | 2013-04-04 | General Electric Company | Turbomachine having a gas flow aeromechanic system and method |
-
2013
- 2013-08-09 US US13/963,689 patent/US9435221B2/en active Active
-
2014
- 2014-07-22 DE DE201410110315 patent/DE102014110315A1/en active Pending
- 2014-08-01 JP JP2014157284A patent/JP6514455B2/en active Active
- 2014-08-07 CH CH01203/14A patent/CH708447A2/en not_active Application Discontinuation
- 2014-08-08 CN CN201410389920.7A patent/CN105019949B/en active Active
Patent Citations (129)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2663493A (en) | 1949-04-26 | 1953-12-22 | A V Roe Canada Ltd | Blading for compressors, turbines, and the like |
US3347520A (en) | 1966-07-12 | 1967-10-17 | Jerzy A Oweczarek | Turbomachine blading |
US3734639A (en) | 1968-01-25 | 1973-05-22 | Gen Motors Corp | Turbine cooling |
US3572962A (en) | 1969-06-02 | 1971-03-30 | Canadian Patents Dev | Stator blading for noise reduction in turbomachinery |
US3643426A (en) | 1969-06-30 | 1972-02-22 | Ingvar Janelid | Powerplant driven by a gas turbine, and a method of operating such a powerplant |
US3745629A (en) | 1972-04-12 | 1973-07-17 | Secr Defence | Method of determining optimal shapes for stator blades |
US4284388A (en) | 1975-11-03 | 1981-08-18 | Polska Akademia Nauk, Instytut Maszyn Przeplywowych | Moving blade for thermic axial turbomachines |
JPS54114619A (en) | 1978-02-28 | 1979-09-06 | Toshiba Corp | Natural frequency adjusting method of turbine blade |
JPS54114618A (en) | 1978-02-28 | 1979-09-06 | Toshiba Corp | Moving and stator blades arranging method of turbine |
US4259842A (en) | 1978-12-11 | 1981-04-07 | General Electric Company | Combustor liner slot with cooled props |
US4504189A (en) | 1982-11-10 | 1985-03-12 | Rolls-Royce Limited | Stator vane for a gas turbine engine |
US4619580A (en) | 1983-09-08 | 1986-10-28 | The Boeing Company | Variable camber vane and method therefor |
US4585395A (en) | 1983-12-12 | 1986-04-29 | General Electric Company | Gas turbine engine blade |
US4616975A (en) | 1984-07-30 | 1986-10-14 | General Electric Company | Diaphragm for a steam turbine |
US4714407A (en) | 1984-09-07 | 1987-12-22 | Rolls-Royce Plc | Aerofoil section members for turbine engines |
US4968216A (en) | 1984-10-12 | 1990-11-06 | The Boeing Company | Two-stage fluid driven turbine |
US4786016A (en) | 1986-04-30 | 1988-11-22 | United Technologies Corporation | Bodies with reduced surface drag |
US4844689A (en) | 1986-07-04 | 1989-07-04 | Rolls-Royce Plc | Compressor and air bleed system |
US4802821A (en) | 1986-09-26 | 1989-02-07 | Bbc Brown Boveri Ag | Axial flow turbine |
US4896510A (en) | 1987-02-06 | 1990-01-30 | General Electric Company | Combustor liner cooling arrangement |
US4809498A (en) | 1987-07-06 | 1989-03-07 | General Electric Company | Gas turbine engine |
US5249922A (en) | 1990-09-17 | 1993-10-05 | Hitachi, Ltd. | Apparatus of stationary blade for axial flow turbine, and axial flow turbine |
US5226278A (en) | 1990-12-05 | 1993-07-13 | Asea Brown Boveri Ltd. | Gas turbine combustion chamber with improved air flow |
US5274991A (en) | 1992-03-30 | 1994-01-04 | General Electric Company | Dry low NOx multi-nozzle combustion liner cap assembly |
US5342170A (en) | 1992-08-29 | 1994-08-30 | Asea Brown Boveri Ltd. | Axial-flow turbine |
US5406786A (en) | 1993-07-16 | 1995-04-18 | Air Products And Chemicals, Inc. | Integrated air separation - gas turbine electrical generation process |
US5749218A (en) | 1993-12-17 | 1998-05-12 | General Electric Co. | Wear reduction kit for gas turbine combustors |
US5486091A (en) | 1994-04-19 | 1996-01-23 | United Technologies Corporation | Gas turbine airfoil clocking |
US5785498A (en) | 1994-09-30 | 1998-07-28 | General Electric Company | Composite fan blade trailing edge reinforcement |
US6598398B2 (en) | 1995-06-07 | 2003-07-29 | Clean Energy Systems, Inc. | Hydrocarbon combustion power generation system with CO2 sequestration |
US6209325B1 (en) | 1996-03-29 | 2001-04-03 | European Gas Turbines Limited | Combustor for gas- or liquid-fueled turbine |
US5813828A (en) | 1997-03-18 | 1998-09-29 | Norris; Thomas R. | Method and apparatus for enhancing gas turbo machinery flow |
US6438961B2 (en) | 1998-02-10 | 2002-08-27 | General Electric Company | Swozzle based burner tube premixer including inlet air conditioner for low emissions combustion |
US6958383B2 (en) | 1998-02-26 | 2005-10-25 | Aventis Pharma S. A. | Streptogramin derivatives, preparation method and compositions containing same |
US6491493B1 (en) | 1998-06-12 | 2002-12-10 | Ebara Corporation | Turbine nozzle vane |
US6626635B1 (en) | 1998-09-30 | 2003-09-30 | General Electric Company | System for controlling clearance between blade tips and a surrounding casing in rotating machinery |
US6174129B1 (en) | 1999-01-07 | 2001-01-16 | Siemens Westinghouse Power Corporation | Turbine vane clocking mechanism and method of assembling a turbine having such a mechanism |
US6345493B1 (en) | 1999-06-04 | 2002-02-12 | Air Products And Chemicals, Inc. | Air separation process and system with gas turbine drivers |
US6428281B1 (en) | 1999-08-18 | 2002-08-06 | Snecma Moteurs | Turbine vane with enhanced profile |
EP1130321A1 (en) | 2000-02-25 | 2001-09-05 | General Electric Company | Combustor liner cooling thimbles and related method |
US6484505B1 (en) | 2000-02-25 | 2002-11-26 | General Electric Company | Combustor liner cooling thimbles and related method |
US7089742B2 (en) | 2000-02-29 | 2006-08-15 | Rolls-Royce Plc | Wall elements for gas turbine engine combustors |
US6584779B2 (en) | 2000-04-19 | 2003-07-01 | General Electric Company | Combustion turbine cooling media supply method |
US6910335B2 (en) | 2000-05-12 | 2005-06-28 | Clean Energy Systems, Inc. | Semi-closed Brayton cycle gas turbine power systems |
US6824710B2 (en) | 2000-05-12 | 2004-11-30 | Clean Energy Systems, Inc. | Working fluid compositions for use in semi-closed brayton cycle gas turbine power systems |
US6435814B1 (en) | 2000-05-16 | 2002-08-20 | General Electric Company | Film cooling air pocket in a closed loop cooled airfoil |
US6446438B1 (en) | 2000-06-28 | 2002-09-10 | Power Systems Mfg., Llc | Combustion chamber/venturi cooling for a low NOx emission combustor |
US6602458B1 (en) | 2000-06-28 | 2003-08-05 | Rubbermaid Incorporated | Reduced flash molding |
US6402458B1 (en) * | 2000-08-16 | 2002-06-11 | General Electric Company | Clock turbine airfoil cooling |
US6543234B2 (en) | 2000-09-11 | 2003-04-08 | General Electric Company | Compressor discharge bleed air circuit in gas turbine plants and related method |
US6442941B1 (en) | 2000-09-11 | 2002-09-03 | General Electric Company | Compressor discharge bleed air circuit in gas turbine plants and related method |
US6527503B2 (en) | 2000-10-23 | 2003-03-04 | Fiatavio S.P.A. | Method of positioning turbine stage arrays, particularly for aircraft engines |
US20020048510A1 (en) | 2000-10-23 | 2002-04-25 | Fiatavio S.P.A. | Method of positioning turbine stage arrays, particularly for aircraft engines |
US6540478B2 (en) | 2000-10-27 | 2003-04-01 | Mtu Aero Engines Gmbh | Blade row arrangement for turbo-engines and method of making same |
US6409126B1 (en) | 2000-11-01 | 2002-06-25 | Lockhead Martin Corporation | Passive flow control of bluff body wake turbulence |
US6887042B2 (en) | 2001-01-12 | 2005-05-03 | Mitsubishi Heavy Industries, Ltd. | Blade structure in a gas turbine |
US20020124572A1 (en) | 2001-03-12 | 2002-09-12 | Anthony Pidcock | Combustion apparatus |
EP1247938A2 (en) | 2001-03-30 | 2002-10-09 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Clocking of stator- or rotorblades |
US6554562B2 (en) | 2001-06-15 | 2003-04-29 | Honeywell International, Inc. | Combustor hot streak alignment for gas turbine engine |
US6905307B2 (en) | 2001-08-10 | 2005-06-14 | Honda Giken Kogyo Kabushiki Kaisha | Stationary vanes for turbines and method for making the same |
US20030136102A1 (en) | 2002-01-22 | 2003-07-24 | Snecma Moteurs | Diffuser for terrestrial or aviation gas turbine |
US6772595B2 (en) | 2002-06-25 | 2004-08-10 | Power Systems Mfg., Llc | Advanced cooling configuration for a low emissions combustor venturi |
USD511377S1 (en) | 2002-07-01 | 2005-11-08 | Donaldson Company, Inc. | Inlet air filter hood module for gas turbine systems |
US6986639B2 (en) | 2002-08-09 | 2006-01-17 | Honda Giken Kogyo Kabushiki Kaisha | Stator blade for an axial flow compressor |
US6899081B2 (en) | 2002-09-20 | 2005-05-31 | Visteon Global Technologies, Inc. | Flow conditioning device |
US20050206196A1 (en) | 2002-09-20 | 2005-09-22 | The Regents Of The University Of California | Apparatus and method for reducing drag of a bluff body in ground effect using counter-rotating vortex pairs |
US7410343B2 (en) | 2002-12-09 | 2008-08-12 | Mitsubishi Heavy Industries, Ltd. | Gas turbine |
US7121792B1 (en) | 2003-03-27 | 2006-10-17 | Snecma Moteurs | Nozzle vane with two slopes |
US6935116B2 (en) | 2003-04-28 | 2005-08-30 | Power Systems Mfg., Llc | Flamesheet combustor |
US20050172607A1 (en) | 2003-05-16 | 2005-08-11 | Koichi Ishizaka | Exhaust diffuser for axial-flow turbine |
EP1482246A1 (en) | 2003-05-30 | 2004-12-01 | Siemens Aktiengesellschaft | Combustion chamber |
US6913441B2 (en) | 2003-09-04 | 2005-07-05 | Siemens Westinghouse Power Corporation | Turbine blade ring assembly and clocking method |
US7373773B2 (en) | 2003-09-04 | 2008-05-20 | Hitachi, Ltd. | Gas turbine installation, cooling air supplying method and method of modifying a gas turbine installation |
US7217101B2 (en) | 2003-10-15 | 2007-05-15 | Alstom Technology Ltd. | Turbine rotor blade for gas turbine engine |
US7007478B2 (en) | 2004-06-30 | 2006-03-07 | General Electric Company | Multi-venturi tube fuel injector for a gas turbine combustor |
US7420662B2 (en) | 2004-08-04 | 2008-09-02 | Colorado State University Research Foundation | Optical diagnostics integrated with laser spark delivery system |
US7412129B2 (en) | 2004-08-04 | 2008-08-12 | Colorado State University Research Foundation | Fiber coupled optical spark delivery system |
US7340129B2 (en) | 2004-08-04 | 2008-03-04 | Colorado State University Research Foundation | Fiber laser coupled optical spark delivery system |
US7574865B2 (en) | 2004-11-18 | 2009-08-18 | Siemens Energy, Inc. | Combustor flow sleeve with optimized cooling and airflow distribution |
US20060101801A1 (en) | 2004-11-18 | 2006-05-18 | Siemens Westinghouse Power Corporation | Combustor flow sleeve with optimized cooling and airflow distribution |
US7758297B2 (en) | 2005-05-10 | 2010-07-20 | Mtu Aero Engines Gmbh | Method for flow optimization in multi-stage turbine-type machines |
US20060283189A1 (en) | 2005-06-15 | 2006-12-21 | General Electric Company | Axial flow sleeve for a turbine combustor and methods of introducing flow sleeve air |
US20070025836A1 (en) | 2005-07-28 | 2007-02-01 | General Electric Company | Cooled shroud assembly and method of cooling a shroud |
US8308112B2 (en) | 2005-10-17 | 2012-11-13 | Textron Innovations Inc. | Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft |
CN101296842A (en) | 2005-10-17 | 2008-10-29 | 贝尔直升机特克斯特龙有限公司 | Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft |
CN1955440A (en) | 2005-10-28 | 2007-05-02 | 中国科学院工程热物理研究所 | Three-D sequential effect maximization method for multi-stage turbomachine |
US7805946B2 (en) | 2005-12-08 | 2010-10-05 | Siemens Energy, Inc. | Combustor flow sleeve attachment system |
US20070130958A1 (en) | 2005-12-08 | 2007-06-14 | Siemens Power Generation, Inc. | Combustor flow sleeve attachment system |
US7762074B2 (en) | 2006-04-04 | 2010-07-27 | Siemens Energy, Inc. | Air flow conditioner for a combustor can of a gas turbine engine |
US7654320B2 (en) | 2006-04-07 | 2010-02-02 | Occidental Energy Ventures Corp. | System and method for processing a mixture of hydrocarbon and CO2 gas produced from a hydrocarbon reservoir |
CN101050722A (en) | 2006-04-07 | 2007-10-10 | 孙敏超 | Changeable outlet flow section turbine jet nozzle ring |
US20070251240A1 (en) | 2006-04-13 | 2007-11-01 | General Electric Company | Forward sleeve retainer plate and method |
US7758306B2 (en) | 2006-12-22 | 2010-07-20 | General Electric Company | Turbine assembly for a gas turbine engine and method of manufacturing the same |
US8286347B2 (en) | 2007-02-27 | 2012-10-16 | Snecma | Method for reducing vibration levels of a bladed wheel in a turbomachine |
US20090320484A1 (en) | 2007-04-27 | 2009-12-31 | Benjamin Paul Lacy | Methods and systems to facilitate reducing flashback/flame holding in combustion systems |
US20090223228A1 (en) | 2007-08-15 | 2009-09-10 | Carey Edward Romoser | Method and apparatus for combusting fuel within a gas turbine engine |
CN101173673A (en) | 2007-11-29 | 2008-05-07 | 北京航空航天大学 | Big and small impeller vane impeller with non-homogeneously distributed blades along circumference and compressor machine |
US20090155062A1 (en) | 2007-12-14 | 2009-06-18 | Snecma | Method of designing a multistage turbine for a turbomachine |
US8083476B2 (en) | 2007-12-14 | 2011-12-27 | Snecma | Method of designing a multistage turbine for a turbomachine |
US7896645B2 (en) | 2008-05-30 | 2011-03-01 | Universal Cleanair Technologies | Three phased combustion system |
US8540490B2 (en) | 2008-06-20 | 2013-09-24 | General Electric Company | Noise reduction in a turbomachine, and a related method thereof |
EP2154431A2 (en) | 2008-08-14 | 2010-02-17 | Alstom Technology Ltd | Thermal machine |
US20100054929A1 (en) * | 2008-09-04 | 2010-03-04 | General Electric Company | Turbine airfoil clocking |
US20100054922A1 (en) * | 2008-09-04 | 2010-03-04 | General Electric Company | Turbine airfoil clocking |
US8297919B2 (en) * | 2008-10-31 | 2012-10-30 | General Electric Company | Turbine airfoil clocking |
US20100111684A1 (en) | 2008-10-31 | 2010-05-06 | General Electric Company | Turbine airfoil clocking |
US20100122538A1 (en) | 2008-11-20 | 2010-05-20 | Wei Ning | Methods, apparatus and systems concerning the circumferential clocking of turbine airfoils in relation to combustor cans and the flow of cooling air through the turbine hot gas flowpath |
US8425185B2 (en) | 2009-02-25 | 2013-04-23 | Hitachi, Ltd. | Transonic blade |
US8307657B2 (en) | 2009-03-10 | 2012-11-13 | General Electric Company | Combustor liner cooling system |
US20110189003A1 (en) | 2009-03-19 | 2011-08-04 | Mitsubishi Heavy Industries, Ltd. | Gas turbine |
US8234872B2 (en) | 2009-05-01 | 2012-08-07 | General Electric Company | Turbine air flow conditioner |
US20100287943A1 (en) | 2009-05-14 | 2010-11-18 | General Electric Company | Methods and systems for inducing combustion dynamics |
US20100326082A1 (en) | 2009-06-30 | 2010-12-30 | Willy Steve Ziminsky | Methods and apparatus for combustor fuel circuit for ultra low calorific fuels |
US20110107766A1 (en) | 2009-11-11 | 2011-05-12 | Davis Jr Lewis Berkley | Combustor assembly for a turbine engine with enhanced cooling |
US20110197586A1 (en) | 2010-02-15 | 2011-08-18 | General Electric Company | Systems and Methods of Providing High Pressure Air to a Head End of a Combustor |
US8516822B2 (en) | 2010-03-02 | 2013-08-27 | General Electric Company | Angled vanes in combustor flow sleeve |
US20110214429A1 (en) | 2010-03-02 | 2011-09-08 | General Electric Company | Angled vanes in combustor flow sleeve |
US20120051894A1 (en) | 2010-08-31 | 2012-03-01 | General Electric Company | Turbine assembly with end-wall-contoured airfoils and preferenttial clocking |
US8707672B2 (en) | 2010-09-10 | 2014-04-29 | General Electric Company | Apparatus and method for cooling a combustor cap |
US20120085100A1 (en) | 2010-10-11 | 2012-04-12 | General Electric Company | Combustor with a Lean Pre-Nozzle Fuel Injection System |
US20120159954A1 (en) | 2010-12-21 | 2012-06-28 | Shoko Ito | Transition piece and gas turbine |
US20120167586A1 (en) | 2011-01-05 | 2012-07-05 | Donald Mark Bailey | Fuel Nozzle Passive Purge Cap Flow |
US20120186255A1 (en) | 2011-01-24 | 2012-07-26 | General Electric Company | System for pre-mixing in a fuel nozzle |
US20120247118A1 (en) | 2011-03-28 | 2012-10-04 | General Electric Company | Combustor crossfire tube |
US20120297785A1 (en) | 2011-05-24 | 2012-11-29 | General Electric Company | System and method for flow control in gas turbine engine |
US20140041357A1 (en) | 2011-10-19 | 2014-02-13 | Anthony J. Malandra | Exhaust diffuser including flow mixing ramp for a gas turbine engine |
US20130115566A1 (en) | 2011-11-04 | 2013-05-09 | General Electric Company | Combustor having wake air injection |
US20140020395A1 (en) | 2012-07-23 | 2014-01-23 | General Electric Company | Method for modifying gas turbine performance |
US20140072433A1 (en) | 2012-09-10 | 2014-03-13 | General Electric Company | Method of clocking a turbine by reshaping the turbine's downstream airfoils |
Non-Patent Citations (4)
Title |
---|
Chinese Office Action issued in connection with corresponding CN Application No. 201310408334.8 on Oct. 30, 2015, 14 pages. |
Extended European Search Report for EP Application No. 12190915.4-1602, dated Feb. 11, 2013, 7 pages. |
Extended European Search Report for EP Application No. 12190923.8-1602, dated Feb. 13, 2013, 6 pages. |
Office Action for CN Application No. 20120369382.6, dated Feb. 25, 2015, 11 pages. |
Also Published As
Publication number | Publication date |
---|---|
CN105019949B (en) | 2018-06-05 |
US20150044017A1 (en) | 2015-02-12 |
CH708447A2 (en) | 2015-02-13 |
JP2015036544A (en) | 2015-02-23 |
CN105019949A (en) | 2015-11-04 |
JP6514455B2 (en) | 2019-05-15 |
DE102014110315A1 (en) | 2015-02-12 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US8297919B2 (en) | Turbine airfoil clocking | |
US9359900B2 (en) | Exhaust diffuser | |
JP2010196563A (en) | Transonic blade | |
EP2410125A1 (en) | Gas turbine | |
EP2586976A2 (en) | Turbine for a turbomachine | |
US10718340B2 (en) | Gas turbine manufacturing method | |
US20180171872A1 (en) | Cooling assembly for a turbine assembly | |
KR20100080421A (en) | Turbine airfoil clocking | |
US10408070B2 (en) | Turbine engine guide vane | |
CN109815624A (en) | A kind of compressor stability boundaris judgment method for considering inlet total pressure distortion and influencing | |
US9435221B2 (en) | Turbomachine airfoil positioning | |
US9500085B2 (en) | Method for modifying gas turbine performance | |
JP5426305B2 (en) | Turbo machine | |
US9759234B2 (en) | Aerodynamic coupling between two annular rows of stationary vanes in a turbine engine | |
JP2018155248A (en) | Turbomachine vane having airfoil designed to provide improved aerodynamic and mechanical properties | |
Stummann et al. | Circumferentially non-uniform flow in the rear stage of a multistage compressor | |
Witteck et al. | Comparison of transient blade row methods for the CFD analysis of a high-pressure turbine | |
JP2010059967A (en) | Method for clocking turbine airfoils | |
CN103670526A (en) | Method of clocking a turbine by reshaping the turbine's downstream airfoils | |
EP3163020B1 (en) | Turbine rotor blade cascade, turbine stage and axial flow turbine | |
US9784286B2 (en) | Flutter-resistant turbomachinery blades | |
JP2018524514A (en) | Turbomachine rotor blade | |
EP2666963B1 (en) | Turbine and method for reducing shock losses in a turbine | |
US9482237B1 (en) | Method of designing a multi-stage turbomachine compressor | |
Kulkarni et al. | Development and applications of a stage stacking procedure |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SMITH, PAUL KENDALL;REEL/FRAME:031009/0486 Effective date: 20130809 |
|
FEPP | Fee payment procedure |
Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 4 |
|
AS | Assignment |
Owner name: GE INFRASTRUCTURE TECHNOLOGY LLC, SOUTH CAROLINA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GENERAL ELECTRIC COMPANY;REEL/FRAME:065727/0001 Effective date: 20231110 |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 8TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1552); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 8 |